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EP1175337B1 - Rotary wing aircraft supplementary power drive system - Google Patents

Rotary wing aircraft supplementary power drive system Download PDF

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Publication number
EP1175337B1
EP1175337B1 EP00930075A EP00930075A EP1175337B1 EP 1175337 B1 EP1175337 B1 EP 1175337B1 EP 00930075 A EP00930075 A EP 00930075A EP 00930075 A EP00930075 A EP 00930075A EP 1175337 B1 EP1175337 B1 EP 1175337B1
Authority
EP
European Patent Office
Prior art keywords
rotor
power
tail
drive system
main
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP00930075A
Other languages
German (de)
French (fr)
Other versions
EP1175337A4 (en
EP1175337A1 (en
Inventor
Frank N. Piasecki
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Individual
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Individual
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Filing date
Publication date
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Publication of EP1175337A4 publication Critical patent/EP1175337A4/en
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Publication of EP1175337B1 publication Critical patent/EP1175337B1/en
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Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B64C27/14—Direct drive between power plant and rotor hub
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8236—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft including pusher propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
    • B64C2027/8272—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising fins, or movable rudders
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T74/00—Machine element or mechanism
    • Y10T74/19—Gearing
    • Y10T74/19023—Plural power paths to and/or from gearing
    • Y10T74/19126—Plural drivers plural driven
    • Y10T74/1913—Bevel

Definitions

  • This invention relates to a supplementary power drive system for providing additional power to the rotor drive system powering the drive shafts of rotary wing aircraft main lifting and tail mounted anti-torque propellers.
  • US 3,255,825 discloses a helicopter powered by three gas turbines, two of which are mounted forward and one aft.
  • the turbines have their power transmitted to a transmission box through their respective drive shafts.
  • the drive shafts are cross-connected through a main spur gear associated with the forward engines and through a connecting spur gear associated with the rear turbine and mounted on a torsion shaft.
  • the tail anti-torque rotor is driven from a power take-off on the torsion shaft.
  • a spur gear angularly rigid with the torsion shaft drives, through an intermediate spur gear, a drive spur gear connected to the drive shaft of the tail rotor.
  • US 3,002,710 also discloses a helicopter powered by three turbines, one on front and two rear turbines.
  • the pair of rear turbines are connected to a coupling gear case disposed at their rear output ends through the medium of two small gears mounted on the end of the turbine shafts and meshing through a pair of free-wheel devices with a central toothed wheel.
  • This central wheel meshes on the one hand with a small pinion and on the other hand with a larger toothed wheel.
  • the small pinion serves the purpose of transmitting the motion to the front and is connected through a shaft with the rear input pinion of the main transmission powering the lifting rotor.
  • the toothed wheel constitutes a power take-off and is connected through an adequate transmission with the anti-torque tail rotor.
  • the supplementary power drive system of this invention bypasses this power absorbing limitation of the main rotor transmission by utilizing the usually installed auxiliary power turbine, normally used for starting the main engine turbines, as a source of additional shaft power to the rotor drive system for driving the tail mounted torque compensating propeller as well as the main rotor if the main rotor transmission can absorb the increased power.
  • a supplemental power transfer unit comprising a one-stage gear train into the tail mounted propeller drive system that drives the tail propeller and extends between the main rotor transmission and the tail propeller and in which a gear of the train connected to the main transmission and meshing with gears connected to the tail propeller drive shaft also is connected to the power output of the auxiliary power turbine. This allows power from the auxiliary power plant to go directly to the tail propeller and bypass the transmission, or is available to the main transmission for driving the main rotor in certain flight modes when the main rotor transmission can absorb the additional power.
  • the supplementary power driving system of this invention can be advantageously used in providing additional power to the power drive system of any type of single rotary wing aircraft having a tail mounted rotor for counteracting the torque of the main rotor
  • this invention is most advantageous when incorporated into the power drive system of compound helicopters having a fixed wing providing a lift in forward flight and a vectored thrust ducted propeller tail assembly, sometimes referred to as a "ring tail.”
  • Aircraft of this type are described in U.S. Patent Nos. 3,138,349; 3,222,012; 3,241,791; 3,260,482; 4,905,932; 5,123,613; 5,131,603 and 5,227,381.
  • the tail assembly of these "ring tail” compound helicopters have a propeller rotatable contained within a duct incorporating rotatable vanes or other provisions for directing the propeller slip stream transversely of the aircraft to establish lateral thrust for counteracting rotor torque in hovering or slow speed flight or directing the slip stream rearwardly of the aircraft to provide forward propulsive thrust in forward flight.
  • a portion of the power is used to drive the tail propeller for anti-torque purposes.
  • Supplying auxiliary power directly to the tail propeller increases the power available to the main rotor for hovering flight without overloading the main rotor transmission.
  • thrust for forward high speed flight being primarily or entirely provided by the tail rotor, supplying power from the auxiliary power plant directly to the tail rotor makes this increased power directly available for forward flight without going through the main rotor transmission.
  • An example for a single rotor, rotary wing aircraft power drive system 10 to which this invention is applicable includes a pair of main engine turbines 11 which provide power to the main transmission 12 for driving the main rotor and for driving the tail propeller 13 through a tail propeller drive system extending between the main transmission 12 and the tail propeller 13.
  • the tail propeller 13 may be the shrouded propeller of a vectored thrust ducted propeller compound helicopter that provides transverse thrust for counteracting main rotor torque and forward propulsive thrust for forward flight of the type illustrated in Figure 1.
  • propeller 13 is also intended to represent the rotor mounted on the tail of conventional single rotor helicopters. Therefore, for purposes of describing this invention, the terms "tail propeller” and “tail rotor” are synonymous in meaning.
  • power from the main turbine engines 11 transmitted through overrunning clutches and reduction gear pinions and drive pinions drives the transmission main bevel gear coupled to a drive shaft driving the planetary gear train that connects to and drives the drive shaft of the main rotor at the design RPM.
  • the tail propeller drive system receives power from the main transmission through a drive pinion meshing with the transmission main bevel gear and delivers it to the tail propeller 13.
  • the tail propeller drive system normally comprises an integral shaft arrangement connecting between a main rotor transmission powered by engine 11 and the tail rotor 13 as indicated in Figure 1.
  • auxiliary power plant usually a turbine
  • main engine drive shaft system or bleeding compressed air from the auxiliary power plant to start the main engines.
  • the supplementary power system of this invention makes power from the auxiliary power plant available to the rotor main drive system of single rotor helicopters without overloading the main rotor transmission by introducing this power from the auxiliary power plant into the rotor main drive system through the tail-propeller drive system into which the supplemental power unit comprising the single stage gear train is incorporated.
  • This supplemental power unit gear train comprises a pair of superimposed meshing spur gears and of which a first one of the gear pairs is connected to the power output shaft of the auxiliary power turbine through an overrunning clutch, a second one of the gear pairs is connected to the transmission connection side of the tail propeller drive system and a third spur gear of the gear train meshing with the second gear of the gear train through an idle gear has a connection to the drive shaft of the tail propeller 13.
  • the power available to the main rotor can be increased for hovering in all types of single rotor helicopters without overloading the main transmission since power for anti-torque is transmitted directly to the tail propeller.
  • power available for forward flight is increased, particularly for high speed, without overloading the main transmission since forward propulsion is provided primarily or entirely by the tail propeller.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transmission Devices (AREA)
  • Retarders (AREA)
  • Auxiliary Drives, Propulsion Controls, And Safety Devices (AREA)
  • Dynamo-Electric Clutches, Dynamo-Electric Brakes (AREA)
  • Radio Relay Systems (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

A supplementary power drive system for providing additional power to the drive system of rotary wing aircraft that powers the aircraft main lifting rotor and tail mounted torque compensating rotor or propeller in a manner as avoids overloading the power capacity of the main rotor transmission. The supplementary power system, utilizing the power of a usually installed auxiliary power plant as a source of additional power, bypasses the main engine powered main rotor transmission in providing power to the tail mounted rotor or propeller and main rotor if the main transmission cannot absorb it. This is accomplished by incorporating a supplemental power transfer unit comprising a one-stage gear train into the tail rotor/propeller drive system that extends from the main transmission to the tail rotor/propeller in which a gear from the gear train connected to the main transmission and meshing with gears connected to the tail rotor/propeller drive shaft also is connected to the power output from the auxiliary power plant. This allows power from the auxiliary power plant to go directly to the tail rotor/propeller and bypass the main transmission, or is available to the main transmission for driving the main rotor in certain flight modes when the main rotor transmission can absorb the additional power.

Description

This invention relates to a supplementary power drive system for providing additional power to the rotor drive system powering the drive shafts of rotary wing aircraft main lifting and tail mounted anti-torque propellers.
BACKGROUND OF THE INVENTION
In the development of fixed wing aircraft as requirements increase for greater weight and performance additional propulsive power is required. This could often be met by the relatively easy expedient of replacing the engines with higher powered engines. However, for rotary wing aircraft this relatively simple expedient is not feasible in most instances since additional power from higher powered engines for increasing aircraft performance must pass through the main rotor transmission which has an upper limit of the amount of power which can be absorbed and is a limiting factor in adding additional power to the main rotor for propulsion and lift. Main rotor transmissions comprise complex power gear trains with severe limitations in the amount of horsepower that the power train can absorb and redesigning a main rotor transmission to accommodate even moderate increases in power is a major and expensive undertaking.
US 3,255,825 discloses a helicopter powered by three gas turbines, two of which are mounted forward and one aft. The turbines have their power transmitted to a transmission box through their respective drive shafts. In the transmission box, the drive shafts are cross-connected through a main spur gear associated with the forward engines and through a connecting spur gear associated with the rear turbine and mounted on a torsion shaft. The tail anti-torque rotor is driven from a power take-off on the torsion shaft. To this end, a spur gear angularly rigid with the torsion shaft drives, through an intermediate spur gear, a drive spur gear connected to the drive shaft of the tail rotor.
US 3,002,710 also discloses a helicopter powered by three turbines, one on front and two rear turbines. The pair of rear turbines are connected to a coupling gear case disposed at their rear output ends through the medium of two small gears mounted on the end of the turbine shafts and meshing through a pair of free-wheel devices with a central toothed wheel. This central wheel meshes on the one hand with a small pinion and on the other hand with a larger toothed wheel. The small pinion serves the purpose of transmitting the motion to the front and is connected through a shaft with the rear input pinion of the main transmission powering the lifting rotor. The toothed wheel constitutes a power take-off and is connected through an adequate transmission with the anti-torque tail rotor.
SUMMARY OF THE INVENTION
The supplementary power drive system of this invention bypasses this power absorbing limitation of the main rotor transmission by utilizing the usually installed auxiliary power turbine, normally used for starting the main engine turbines, as a source of additional shaft power to the rotor drive system for driving the tail mounted torque compensating propeller as well as the main rotor if the main rotor transmission can absorb the increased power. This is accomplished by incorporating a supplemental power transfer unit comprising a one-stage gear train into the tail mounted propeller drive system that drives the tail propeller and extends between the main rotor transmission and the tail propeller and in which a gear of the train connected to the main transmission and meshing with gears connected to the tail propeller drive shaft also is connected to the power output of the auxiliary power turbine. This allows power from the auxiliary power plant to go directly to the tail propeller and bypass the transmission, or is available to the main transmission for driving the main rotor in certain flight modes when the main rotor transmission can absorb the additional power.
Whereas the supplementary power driving system of this invention can be advantageously used in providing additional power to the power drive system of any type of single rotary wing aircraft having a tail mounted rotor for counteracting the torque of the main rotor, this invention is most advantageous when incorporated into the power drive system of compound helicopters having a fixed wing providing a lift in forward flight and a vectored thrust ducted propeller tail assembly, sometimes referred to as a "ring tail." Aircraft of this type are described in U.S. Patent Nos. 3,138,349; 3,222,012; 3,241,791; 3,260,482; 4,905,932; 5,123,613; 5,131,603 and 5,227,381. The tail assembly of these "ring tail" compound helicopters have a propeller rotatable contained within a duct incorporating rotatable vanes or other provisions for directing the propeller slip stream transversely of the aircraft to establish lateral thrust for counteracting rotor torque in hovering or slow speed flight or directing the slip stream rearwardly of the aircraft to provide forward propulsive thrust in forward flight. For hovering flight, although the major portion of the main engine power passing through the main rotor transmission is used to drive the main rotor, a portion of the power is used to drive the tail propeller for anti-torque purposes. Supplying auxiliary power directly to the tail propeller increases the power available to the main rotor for hovering flight without overloading the main rotor transmission. Similarly, thrust for forward high speed flight being primarily or entirely provided by the tail rotor, supplying power from the auxiliary power plant directly to the tail rotor makes this increased power directly available for forward flight without going through the main rotor transmission.
BRIEF DESCRIPTION OF THE DRAWINGS
  • Figure 1 is a side elevation, partially in section, of a conventional single rotor helicopter having a tail rotor mounted for rotation about a transversely extending axis for counteracting main rotor torque is an example of helicopters for utilizing the supplementary power drive system of this invention.
  • Figure 2 is a perspective view of the compound helicopter with a vectored thrust ducted propeller tail assembly described in U.S. Patent 4,905,932 is the category of helicopters in which the supplementary power drive of this invention is most useful.
    • DETAILED DESCRIPTION OF THE INVENTION
    An example for a single rotor, rotary wing aircraft power drive system 10 to which this invention is applicable includes a pair of main engine turbines 11 which provide power to the main transmission 12 for driving the main rotor and for driving the tail propeller 13 through a tail propeller drive system extending between the main transmission 12 and the tail propeller 13. The tail propeller 13 may be the shrouded propeller of a vectored thrust ducted propeller compound helicopter that provides transverse thrust for counteracting main rotor torque and forward propulsive thrust for forward flight of the type illustrated in Figure 1. For purposes of describing the application of this invention to conventional single main rotor helicopters having a tail rotor of the type illustrated in Figure 2, propeller 13 is also intended to represent the rotor mounted on the tail of conventional single rotor helicopters. Therefore, for purposes of describing this invention, the terms "tail propeller" and "tail rotor" are synonymous in meaning. In an embodiment of the invention, power from the main turbine engines 11 transmitted through overrunning clutches and reduction gear pinions and drive pinions drives the transmission main bevel gear coupled to a drive shaft driving the planetary gear train that connects to and drives the drive shaft of the main rotor at the design RPM. The tail propeller drive system receives power from the main transmission through a drive pinion meshing with the transmission main bevel gear and delivers it to the tail propeller 13. In conventional single main and tail rotor helicopters and compound shrouded propeller tail duct "ring tail" helicopters, to which the supplementary drive system of this invention is applicable, the tail propeller drive system normally comprises an integral shaft arrangement connecting between a main rotor transmission powered by engine 11 and the tail rotor 13 as indicated in Figure 1.
    It is common practice to utilize an installed auxiliary power plant, usually a turbine, for starting the main engines of conventional single rotor and compound "ring tail" helicopters by connecting the auxiliary power turbine into the main engine drive shaft system or bleeding compressed air from the auxiliary power plant to start the main engines. The supplementary power system of this invention makes power from the auxiliary power plant available to the rotor main drive system of single rotor helicopters without overloading the main rotor transmission by introducing this power from the auxiliary power plant into the rotor main drive system through the tail-propeller drive system into which the supplemental power unit comprising the single stage gear train is incorporated. This supplemental power unit gear train comprises a pair of superimposed meshing spur gears and of which a first one of the gear pairs is connected to the power output shaft of the auxiliary power turbine through an overrunning clutch, a second one of the gear pairs is connected to the transmission connection side of the tail propeller drive system and a third spur gear of the gear train meshing with the second gear of the gear train through an idle gear has a connection to the drive shaft of the tail propeller 13. This allows power from the auxiliary power plant to go directly to the tail propeller, bypassing the main rotor transmission entirely or, in certain flight modes a portion can be used to drive the main rotor since the tail propeller drive system and the main transmission 12 are interconnected throughout all flight modes of the helicopter. Thus, the power available to the main rotor can be increased for hovering in all types of single rotor helicopters without overloading the main transmission since power for anti-torque is transmitted directly to the tail propeller. In compound "ring tail" helicopters power available for forward flight is increased, particularly for high speed, without overloading the main transmission since forward propulsion is provided primarily or entirely by the tail propeller.
    It should be understood that the foregoing disclosure involves a preferred and typical embodiment of the invention and that numerous modifications or alterations therein would be obvious and made by those of normal skill in the art without departing from the scope of the invention as set forth in the appendant claims.

    Claims (5)

    1. A rotary wing aircraft rotor drive system for driving the aircraft lifting rotor and tail mounted torque compensating rotor (13) comprising:
      a main transmission powered by main engines (11) for delivering power to the lifting rotor and the tail rotor and having a direct connection to a drive shaft of the lifting rotor and a power take-off connection connected to a tail rotor drive system of the aircraft extending between said main transmission (12) and a drive shaft of the tail rotor,
      and a supplementary power drive system for providing additionnal power to said rotor drive system comprising:
      an auxiliary power plant adapted for mounting on said aircraft and adapted for starting the main engines (11)
      power transfer means-connected to said auxiliary power plant and incorporated into said tail rotor drive system between said transmission power take-off connection and said tail rotor drive shaft comprising:
      a gear train comprising a plurality of gears arranged in series driving communication with one another and in which respective-ones of a pair of gears of said train are rotatably connected respectively through said tail rotor drive system to said tail rotor drive shaft and to said transmission power take-off connection and a third one of said gears of said train in series driving communication with said pair of gears is rotatably connected to the output of said auxiliary power plant, whereby power from said auxiliary power plant is delivered by said third and pair of gears of said gear train through said tail rotor drive system to said tail rotor drive shaft and transmission in amounts as are absorbable by the respective tail and lifting rotors in establishing the desired aircraft flight mode.
    2. The drive system of claim 1 wherein said third gear is located adjacent said pair of gears and is in driving communication with one of said pair of gears.
    3. The drive system of Claim 2 wherein said third gear is adjacent to in direct driving connection with the gear of said gear pair that is rotatably connected to said transmission power take-off connection.
    4. The drive system of claim 3 wherein said gears are spur gears and an idler gear is interposed between each of said gears of said gear pair.
    5. The drive system of one of the preceding claims wherein main transmission (12) is indirectly connected to a drive shaft of the aircraft tail mounted torque compensating rotor (13) through the tail rotor drive system of the aircraft.
    EP00930075A 1999-05-06 2000-02-22 Rotary wing aircraft supplementary power drive system Expired - Lifetime EP1175337B1 (en)

    Applications Claiming Priority (3)

    Application Number Priority Date Filing Date Title
    US305948 1999-05-06
    US09/305,948 US6098921A (en) 1999-05-06 1999-05-06 Rotary wing aircraft supplementary power drive system
    PCT/US2000/005072 WO2000068075A1 (en) 1999-05-06 2000-02-22 Rotary wing aircraft supplementary power drive system

    Publications (3)

    Publication Number Publication Date
    EP1175337A1 EP1175337A1 (en) 2002-01-30
    EP1175337A4 EP1175337A4 (en) 2002-07-24
    EP1175337B1 true EP1175337B1 (en) 2005-02-09

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    Family Applications (1)

    Application Number Title Priority Date Filing Date
    EP00930075A Expired - Lifetime EP1175337B1 (en) 1999-05-06 2000-02-22 Rotary wing aircraft supplementary power drive system

    Country Status (8)

    Country Link
    US (1) US6098921A (en)
    EP (1) EP1175337B1 (en)
    AT (1) ATE288850T1 (en)
    AU (1) AU4795800A (en)
    CA (1) CA2363090C (en)
    DE (1) DE60018054T2 (en)
    ES (1) ES2235881T3 (en)
    WO (1) WO2000068075A1 (en)

    Cited By (1)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US9353642B2 (en) 2012-11-26 2016-05-31 Airbus Helicopters Rotary wing aircraft having two main engines together with a less powerful secondary engine, and a corresponding method

    Families Citing this family (24)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US7434764B2 (en) * 2005-12-02 2008-10-14 Sikorsky Aircraft Corporation Variable speed gearbox with an independently variable speed tail rotor system for a rotary wing aircraft
    WO2010140994A1 (en) * 2009-06-03 2010-12-09 Drachko Yevgeniy Fedorovich Method for transporting an aircraft and a coaxial-rotor aircraft
    FR2952907B1 (en) * 2009-11-26 2011-12-09 Eurocopter France MOTOR INSTALLATION, HELICOPTER COMPRISING SUCH A MOTOR INSTALLATION, AND METHOD IMPLEMENTED BY THIS MOTOR INSTALLATION
    FR2980771B1 (en) * 2011-09-29 2014-10-31 Eurocopter France HYBRID AIRCRAFT WITH ROTATING WING
    US9038801B2 (en) * 2012-06-15 2015-05-26 Hamilton Sundstrand Corporation Clutch with pressure sustaining system
    FR2992024B1 (en) * 2012-06-15 2017-07-21 Turbomeca METHOD AND ARCHITECTURE OF OPTIMIZED ENERGY TRANSFER BETWEEN AN AUXILIARY POWER MOTOR AND THE MAIN ENGINES OF A HELICOPTER
    US9297290B2 (en) * 2012-10-10 2016-03-29 Sikorsky Aircraft Corporation Rotary wing aircraft having collocated exhaust duct and propeller shaft
    US10562641B2 (en) * 2012-10-10 2020-02-18 Sikorsky Aircraft Corporation AFT exhaust system for rotary wing aircraft
    US9528375B2 (en) * 2012-11-30 2016-12-27 Sikorsky Aircraft Corporation Non-uniform blade distribution for rotary wing aircraft
    WO2016014301A1 (en) * 2014-07-21 2016-01-28 Sikorsky Aircraft Corporation Multi-speed gearbox for tail rotor of a compound helicopter
    CN104229133A (en) * 2014-08-26 2014-12-24 中国直升机设计研究所 Double-rotor-wing driving mechanism
    US10822076B2 (en) 2014-10-01 2020-11-03 Sikorsky Aircraft Corporation Dual rotor, rotary wing aircraft
    WO2016053408A1 (en) 2014-10-01 2016-04-07 Sikorsky Aircraft Corporation Acoustic signature variation of aircraft utilizing a clutch
    CN105691607A (en) * 2015-10-13 2016-06-22 中科新松有限公司 Single-direction shock absorption device for motor of multi-rotor aircraft
    FR3055883B1 (en) * 2016-09-09 2019-03-29 Airbus Helicopters MECHANICAL SYSTEM FOR TRANSMITTING A MOVEMENT AND AIRCRAFT EQUIPPED WITH A CORRESPONDING SYSTEM
    US11174015B2 (en) 2019-02-05 2021-11-16 Textron Innovations Inc. Multimode clutch assemblies having engagement status sensors
    US11174014B2 (en) 2019-02-05 2021-11-16 Textron Innovations Inc. Failsafe multimode clutch assemblies for rotorcraft
    US11174013B2 (en) 2019-02-05 2021-11-16 Textron Innovations Inc. Failsafe multimode clutch assemblies for rotorcraft
    US12049304B2 (en) 2019-02-05 2024-07-30 Textron Innovations Inc. Tail rotor isolation systems for rotorcraft
    US10788088B2 (en) 2019-02-05 2020-09-29 Bell Textron Inc. Multimode powertrains for rotorcraft
    US10793284B2 (en) 2019-02-05 2020-10-06 Bell Textron Inc. Multimode clutch assemblies for rotorcraft
    US11708868B2 (en) 2019-02-13 2023-07-25 Textron Innovations Inc. Failsafe multimode clutch assemblies for rotorcraft
    US11613375B2 (en) 2019-05-16 2023-03-28 Textron Innovations Inc. Dual motor input with overrunning clutch
    US11104430B2 (en) 2019-09-27 2021-08-31 Textron Innovations Inc. Multimode powertrains for multi engine rotorcraft

    Family Cites Families (11)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US3002710A (en) * 1956-05-15 1961-10-03 Sud Aviation Helicopters
    FR1325704A (en) * 1962-03-14 1963-05-03 Sud Aviation Further development of gearboxes for single-rotor helicopters with several turbines
    US3977632A (en) * 1974-02-18 1976-08-31 Westland Aircraft Limited Helicopter power transmission systems
    US4632337A (en) * 1981-09-21 1986-12-30 Hughes Helicopters, Inc. Helicopter rotor transmission systems
    US4489625A (en) * 1982-11-23 1984-12-25 Transmission Research, Inc. Split torque transmission
    FR2568541B1 (en) * 1984-08-06 1987-03-20 Aerospatiale MAIN TRANSMISSION BOX FOR TWIN-MOTOR HELICOPTER
    GB8625712D0 (en) * 1986-10-28 1987-03-18 Westland Plc Transmission system
    US5271295A (en) * 1990-12-12 1993-12-21 Aerospatiale Societe Nationale Industrielle Mechanism for transmitting power between a driving shaft and two assemblies to be driven
    US5131603A (en) * 1991-05-02 1992-07-21 Piasecki Aircraft Corporation Rotary wing aircraft split segmented duct shrouded propeller tail assembly
    JP3029981B2 (en) * 1995-04-27 2000-04-10 株式会社コミュータヘリコプタ先進技術研究所 Helicopter power transmission
    IT1293408B1 (en) * 1997-07-04 1999-03-01 Finmeccanica Spa METHOD OF SURVEILLANCE OF A TRANSMISSION UNIT IN A VEHICLE EQUIPPED WITH ACCELEROMETRIC SENSORS, ESPECIALLY IN A HELICOPTER.

    Cited By (2)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US9353642B2 (en) 2012-11-26 2016-05-31 Airbus Helicopters Rotary wing aircraft having two main engines together with a less powerful secondary engine, and a corresponding method
    CN103921938B (en) * 2012-11-26 2017-04-12 空客直升机 Rotary-wing aircraft provided with two main engines and one less-powerful secondary engine and method

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    US6098921A (en) 2000-08-08
    CA2363090C (en) 2006-01-17
    ATE288850T1 (en) 2005-02-15
    CA2363090A1 (en) 2000-11-16
    EP1175337A4 (en) 2002-07-24
    ES2235881T3 (en) 2005-07-16
    AU4795800A (en) 2000-11-21
    WO2000068075A1 (en) 2000-11-16
    DE60018054T2 (en) 2006-02-09
    DE60018054D1 (en) 2005-03-17
    EP1175337A1 (en) 2002-01-30
    WO2000068075A8 (en) 2002-07-25

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